CN108104954B - A kind of turboshaft engine power rating monitoring method - Google Patents
A kind of turboshaft engine power rating monitoring method Download PDFInfo
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- CN108104954B CN108104954B CN201711247158.9A CN201711247158A CN108104954B CN 108104954 B CN108104954 B CN 108104954B CN 201711247158 A CN201711247158 A CN 201711247158A CN 108104954 B CN108104954 B CN 108104954B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
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Abstract
The present invention relates to helicopter engine security fields, it is related to a kind of turboshaft engine power rating monitoring method, include the following steps: to measure predetermined time interval range intrinsic motivation torque, power whirlpool to fall all data of temperature before revolving speed, power turbine, rotating speed of gas compressor, atmospheric temperature and each parameter of pressure height, and the difference of maximum value and minimum value, above-mentioned all data are as quasi-steady state data segment；It is directed at steady state data section and carries out valuation；Calculate under standard state temperature and rotating speed of gas compressor before the power of engine, power turbine；Calculating acquires the actual power of standard state engine and the difference of anticipating power；When the difference in step 4 is less than predetermined value, the alarm of engine power exception is provided.Turboshaft engine power rating monitoring method of the present invention, the difference of real-time display engine actual power and anticipating power provide the alarm of engine power exception if the difference is less than preset a certain numerical value.
Description
Technical field
The present invention relates to helicopter engine security fields, are related to a kind of turboshaft engine power rating monitoring method.
Background technique
The real output of engine is extremely important to the every flying quality for guaranteeing helicopter, with using the time
Accumulation, the real output of engine can be decayed.Currently, each model helicopter is that monitoring engine power declines both at home and abroad
Subtract trend, it is safe to ensure that engine uses, and provide foundation for engine maintenance, need to engine every flight regular hour
Carry out power assurance checkout facility.
But current engine power guarantees that checkout facility cannot monitor the attenuation trend of engine power at any time.
Summary of the invention
The object of the present invention is to provide a kind of turboshaft engine power rating monitoring methods, at least to solve current hair
Motivation power assurance checkout facility cannot monitor the problem of attenuation trend of engine power at any time.
The technical scheme is that
A kind of turboshaft engine power rating monitoring method, includes the following steps:
The temperature before revolving speed Npt, power turbine Step 1: measurement predetermined time interval range intrinsic motivation torque Q, power whirlpool fall
All data of ITT, rotating speed of gas compressor Ng, atmospheric temperature Tamb and each parameter of pressure height Hp are spent, then choose each ginseng respectively
The corresponding maximum value of number and minimum value, using the difference of maximum value and minimum value as variable quantity, respectively Δ Q, Δ Npt, Δ
ITT, Δ Ng, Δ Tamb, Δ Hp, and judge to be respectively smaller than predetermined variation as Δ Q, Δ Npt, Δ ITT, Δ Ng, Δ Tamb, Δ Hp
Measure εiWhen (i=1,2,3,4,5,6), using above-mentioned all data as quasi-steady state data segment；
Step 2: (1) carries out valuation to the quasi-steady state data segment respectively according to the following formula:
Obtain engine torque Q, power whirlpool is fallen temperature ITT, rotating speed of gas compressor Ng, big temperature before revolving speed Npt, power turbine
Degree Tamb and pressure height Hp respectively corresponds valuation
Wherein, xiData for the quasi-steady state data segment are [x1 K xn],The valuation of data；ωiFor weight system
Number, is obtained by following formula (2):
Wherein, ΔiThe bias of each data point in the quasi-steady state data segment, is obtained by following formula (3):
Wherein, σ is variance, is obtained by following formula (4):
Step 3: according to the following formula (5), (6), (7) calculate standard state under engine power P wN, power turbine
Preceding temperature ITTN (K) and rotating speed of gas compressor NgN:
Wherein, θ is temperature ratio；Δ is pressure ratio；PwWith reference toFor the corresponding main reducing gear output power of 100% torque；NptWith reference to
It falls revolving speed for the corresponding engine power whirlpool of 100% torque；
Step 4: (8), (9) calculate the actual power and anticipating power for acquiring standard state engine according to the following formula
Difference:
Δ PwN (ITTN)=PwN (ITTN)-PwIt is expected that(ITTN) (8)；
Δ PwN (NgN)=PwN (NgN)-PwIt is expected that(NgN) (9)；
PwIt is expected thatIt (ITTN) is that temperature is the minimum guarantee performance of the corresponding engine of ITTN, Pw before power turbineIt is expected that(NgN) it is
The minimum guarantee performance of the corresponding engine of rotating speed of gas compressor NgN；
Step 5: providing the alarm of engine power exception when the difference DELTA PwN in step 4 is less than predetermined value.
Optionally, in the step 2, variances sigma is derived by by following formula (10):
Optionally, in the step 3, pressure ratio Δ obtains according to the following formula (11):
Optionally, in the step 3, temperature ratio θ is obtained according to the following formula (12):
Optionally, the predetermined time interval is 10s.
Optionally, in the step 5, the predetermined value is greater than 0.
Invention effect:
Turboshaft engine power rating monitoring method of the invention, can real-time monitoring engine power state, have in time,
Accurately, reliably the advantages that, may replace traditional engine power and guarantee checkout facility, save the time, saves human and material resources.
Detailed description of the invention
Fig. 1 is turboshaft engine power rating monitoring method flow chart of steps of the present invention.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
1 pair of turboshaft engine power rating monitoring method of the present invention is described in further details with reference to the accompanying drawing.
The present invention provides a kind of turboshaft engine power rating monitoring methods, include the following steps:
Step 1: major parameter needed for judging engine power state falls revolving speed for engine torque Q (%), power whirlpool
Temperature ITT (DEG C), rotating speed of gas compressor Ng (r/min), atmospheric temperature Tamb (DEG C) and pressure before Npt (r/min), power turbine
Height Hp (m) therefore measures all data of above-mentioned each parameter within the scope of predetermined time interval, then chooses each parameter pair respectively
The maximum value and minimum value answered, using the difference of maximum value and minimum value as variable quantity, respectively Δ Q, Δ Npt, Δ ITT, Δ
Ng, Δ Tamb, Δ Hp, and judge to be respectively smaller than predetermined variation amount ε as Δ Q, Δ Npt, Δ ITT, Δ Ng, Δ Tamb, Δ Hpi(i
=1,2,3,4,5,6) when, using above-mentioned all data as quasi-steady state data segment.In the present embodiment, preferably in helicopter flight mistake
Cheng Zhong records each flight parameter in real time, the variable quantity ε of each parameter in any 10s (i.e. measurement predetermined time interval)i(i=1,2,
3,4,5,6) meet formula (1)~formula (6), then the data in this time can be used as the standard for the power rating for judging engine surely
State data.
Specific variable quantity formula is as follows:
Δ Q=Qmax-Qmin< ε1；
Δ Npt=Nptmax-Nptmin< ε2；
Δ ITT=ITTmax-ITTmin< ε3；
Δ Ng=Ngmax-Ngmin< ε4；
Δ Tmab=Tmabmax-Tmabmin< ε5；
Δ Hp=Hpmax-Hpmin< ε6。
Step 2: (1) is respectively aligned to the progress valuation of steady state data section according to the following formula:
Obtain engine torque Q, power whirlpool is fallen temperature ITT, rotating speed of gas compressor Ng, big temperature before revolving speed Npt, power turbine
Degree Tamb and pressure height Hp respectively corresponds valuation
Wherein, xiSubject to steady state data section data be [x1 K xn],The valuation of data；ωiFor weight coefficient, pass through
Following formula (2) obtains:
Wherein, ΔiThe bias of each data point in the quasi-steady state data segment, is obtained by following formula (3):
Wherein, σ is variance, and variances sigma is derived by by following formula (10):
σ formula (4) is as follows:
Step 3: (5), (6), (7) calculate under standard state (15 DEG C of pressure height 0m, atmospheric temperature) according to the following formula
Temperature ITTN and rotating speed of gas compressor NgN before the power P wN of engine, power turbine:
Wherein, θ is temperature ratio；Δ is pressure ratio；PwWith reference toFor the corresponding main reducing gear output power of 100% torque；NptWith reference to
It falls revolving speed for the corresponding engine power whirlpool of 100% torque；
Wherein, pressure ratio Δ obtains according to the following formula (11):
Temperature ratio θ is obtained according to the following formula (12):
Step 4: (8), (9) calculate real output and the expection for acquiring any time engine according to the following formula
The difference of power:
Δ PwN (ITTN)=PwN (ITTN)-PwIt is expected that(ITTN) (8)；
Δ PwN (NgN)=PwN (NgN)-PwIt is expected that(NgN) (9)；
PwIt is expected thatIt (ITTN) is that temperature is the minimum guarantee performance of the corresponding engine of ITTN, Pw before power turbineIt is expected that(NgN) it is
The minimum guarantee performance of the corresponding engine of rotating speed of gas compressor NgN.
Step 5: providing the alarm of engine power exception when the difference DELTA PwN in step 4 is less than predetermined value.This
In embodiment, preferably predetermined value is greater than 0.
Turboshaft engine power rating monitoring method of the present invention, real-time display engine actual power and anticipating power it
Difference, if the difference be less than preset a certain numerical value, provide the alarm of engine power exception, have in time, accurately,
The advantages that reliable, may replace traditional engine power and guarantee checkout facility, save the time, saves human and material resources.
The specific example of turboshaft engine power rating monitoring method of the present invention is as follows:
The data that the following length is 10 seconds are measured, as shown in the table:
The example data that 1 length of table is 10 seconds
1), quasi-steady state data identify:
It is as shown in the table to acquire maximum value and minimum value of each data item in 10 seconds, can determine whether that example data meet threshold value
Steady state data subject to it is required that:
Maximum value and minimum value in 2 each data item of table 10 seconds
In 3 each data item of table 10 seconds whether subject to steady state judgment result
2), valuation calculation method
With temperature ITT data instance before power turbine, its valuation is asked；
Valuation to data isFirst time iteration can be substituted with arithmetic average, it may be assumed that
Data can then be acquired to the variance of present valuation are as follows:
Calculate the bias Δ of each data pointiWith weight coefficient ωi, to each data point xiOffset and weight system
Number is as shown in the table:
Table 4 iterates to calculate for the first time obtain power turbine before temperature ITT data offset and weight coefficient
Then new data valuation are as follows:
After iteration, the valuation ITT for obtaining temperature before power turbine is 695.96 DEG C, the corresponding offset of each data point
It is as shown in the table with weight coefficient:
Temperature ITT data offset and weight coefficient before power turbine are obtained after 5 iteration convergence of table
Valuation in 6 each data item of table 10 seconds:
3), engine power abnormality alarming:
It, can be in the hope of standard state (15 DEG C of pressure height 0m, atmospheric temperature) engine according to the above-mentioned valuation acquired
Temperature ITTN (K) and rotating speed of gas compressor NgN (r/min) before power P wN (kW), power turbine, wherein the corresponding master of 100% torque
Retarder output power PwWith reference toFor 1300kW, fall revolving speed Npt in 100% torque corresponding engine power whirlpoolWith reference toIt is 100%.
Known anticipating power PwIt is expected thatIt (ITTN) is 552kW, PwIt is expected thatIt (NgN) is 560kW.
Therefore, the difference of actual power and anticipating power are as follows:
Δ PwN (ITTN)=PwN (ITTN)-PwIt is expected that(ITTN)=10.76kW；
Δ PwN (NgN)=PwN (NgN)-PwIt is expected that(NgN)=18.765kW；
Difference DELTA PwN is less than preset numerical value, without providing the alarm of engine power exception.
In conclusion turboshaft engine power rating monitoring method of the invention, the statistics first based on existing test flight data
More meet actual valuation calculation method of taking a flight test as a result, establishing；Real-time display engine actual power and anticipating power again；Finally
The alarm of engine power exception is provided in time.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
It is included within the scope of the present invention.Therefore, protection scope of the present invention should be with the scope of protection of the claims
It is quasi-.
Claims (6)
1. a kind of turboshaft engine power rating monitoring method, which comprises the steps of:
The temperature before revolving speed Npt, power turbine Step 1: measurement predetermined time interval range intrinsic motivation torque Q, power whirlpool fall
ITT, rotating speed of gas compressor Ng, atmospheric temperature Tamb and each parameter of pressure height Hp all data, then choose each parameter respectively
Corresponding maximum value and minimum value, using the difference of maximum value and minimum value as variable quantity, respectively Δ Q, Δ Npt, Δ ITT,
Δ Ng, Δ Tamb, Δ Hp, and judge to be respectively smaller than predetermined variation amount ε as Δ Q, Δ Npt, Δ ITT, Δ Ng, Δ Tamb, Δ Hpi
When (i=1,2,3,4,5,6), using above-mentioned all data as quasi-steady state data segment；
Step 2: (1) carries out valuation to the quasi-steady state data segment respectively according to the following formula:
Obtain engine torque Q, power whirlpool is fallen temperature ITT, rotating speed of gas compressor Ng, atmospheric temperature before revolving speed Npt, power turbine
Tamb and pressure height Hp respectively correspond valuation
Wherein, xiData for the quasi-steady state data segment are [x1 K xn],The valuation of data；ωiFor weight coefficient, pass through
Following formula (2) obtains:
Wherein, ΔiThe bias of each data point in the quasi-steady state data segment, is obtained by following formula (3):
Wherein, σ is variance, is obtained by following formula (4):
Step 3: warm before the power P wN of engine, power turbine under (5), (6), (7) calculating standard state according to the following formula
Spend ITTN and rotating speed of gas compressor NgN:
Wherein, θ is temperature ratio；Δ is pressure ratio；PwWith reference toFor the corresponding main reducing gear output power of 100% torque；NptWith reference toFor
Fall revolving speed in 100% torque corresponding engine power whirlpool；
Step 4: (8), (9) calculating acquire the actual power of standard state engine and the difference of anticipating power according to the following formula:
Δ PwN (ITTN)=PwN (ITTN)-PwIt is expected that(ITTN) (8)；
Δ PwN (NgN)=PwN (NgN)-PwIt is expected that(NgN) (9)；
PwIt is expected thatIt (ITTN) is that temperature is the minimum guarantee performance of the corresponding engine of ITTN, Pw before power turbineIt is expected thatIt (NgN) is to calm the anger
The minimum guarantee performance of the corresponding engine of machine revolving speed NgN；
Step 5: providing the alarm of engine power exception when the difference DELTA PwN in step 4 is less than predetermined value.
2. turboshaft engine power rating monitoring method according to claim 1, which is characterized in that in the step 2
In, variances sigma is derived by by following formula (10):
3. turboshaft engine power rating monitoring method according to claim 1, which is characterized in that in the step 3
In, pressure ratio Δ obtains according to the following formula (11):
4. turboshaft engine power rating monitoring method according to claim 1, which is characterized in that in the step 3
In, temperature ratio θ is obtained according to the following formula (12):
5. turboshaft engine power rating monitoring method according to claim 1, which is characterized in that between the predetermined time
It is divided into 10s.
6. turboshaft engine power rating monitoring method according to claim 1, which is characterized in that in the step 5
In, the predetermined value is greater than 0.
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